Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Method for the manufacture of a fibre composite component, a reinforcement element and also a fibre composite component

a technology of fibre composite components and components, applied in the direction of transportation and packaging, other domestic articles, chemistry apparatus and processes, etc., can solve the problems of increasing assembly costs and the weight of the fuselage shell, and achieve the effect of improving adhesive bonded joints and/or bonding and high loads

Active Publication Date: 2018-06-19
AIRBUS OPERATIONS GMBH
View PDF17 Cites 0 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The invention is a method for making a fibre composite component with improved adhesive bonded joints and the ability to withstand high loads. A separate reinforcement element is integrated into the component, allowing for individual adjustment of the bonding surface and optimal force transfer. The reinforcement element can be cured before positioning it in the bonding region for ease of manipulation. The reinforcement element prevents delaminations and is protected by removable fibre layers that compensate for tolerances. Overall, this method allows for the creation of stronger and more durable fibre composite components.

Problems solved by technology

However, the rivets increase the assembly costs and the weight of the fuselage shell.

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Method for the manufacture of a fibre composite component, a reinforcement element and also a fibre composite component
  • Method for the manufacture of a fibre composite component, a reinforcement element and also a fibre composite component
  • Method for the manufacture of a fibre composite component, a reinforcement element and also a fibre composite component

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0032]FIG. 1 shows an inventive fibre composite component 1, with a base element 2, to which a multiplicity of ancillary elements 4, 6 are connected. The fibre composite component 1 is, for example, a shell component, in particular a fuselage shell of an aircraft fuselage, with a skin field, which is stiffened by means of longitudinal stiffeners or stringers, wherein the ancillary elements 4, 6 represent the stringers, and the base element 2 represents the skin field.

[0033]The base element 2 is a shell-type fibre composite element and consists preferably of a multiplicity of fibre webs, which in a laying process such as ATL (Automatic Tape Laying) or FPL (Fibre Placement Laying) have been laid down on a mould surface, not shown, in a plurality of layers and orientations. The fibre webs consist of carbon fibre mats arranged in a thermosetting or thermoplastic resin matrix and are preferably so-called prepregs. Alternatively, however, fibre mats of glass fibres, aramide fibres and sim...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

PropertyMeasurementUnit
resistanceaaaaaaaaaa
weightaaaaaaaaaa
corrosionaaaaaaaaaa
Login to View More

Abstract

A method for the manufacture of a fiber composite component with a base element, and with at least one ancillary element bonded to the base element. A reinforcement element is introduced in at least one bonding region of the base element or the ancillary element for purposes of developing a bonding surface for the ancillary element or the base element. A reinforcement element with fiber sections, the ends of which emanate from a bonding surface is provided. A fiber composite component is provided with a base element, in the bonding regions of which reinforcement elements are introduced, on the bonding surfaces of which ancillary elements are bonded with one such.

Description

CROSS-REFERENCES TO RELATED APPLICATIONS[0001]This application claims the benefit of the U.S. Provisional Application No. 61 / 472,640, filed on Apr. 7, 2011, and of the German patent application No. 10 2011 006 977.1 filed on Apr. 7, 2011, the entire disclosures of which are incorporated herein by way of reference.BACKGROUND OF THE INVENTION[0002]The invention concerns a method for the manufacture of a fibre composite component, a reinforcement element for purposes of developing a bonding surface, and also a fibre composite component manufactured in accordance with such a method.[0003]Shell components (e.g. fuselage and wing shells) of aircraft are composed as a rule from a shell-type skin field and from longitudinal stiffeners. The longitudinal stiffeners or ancillary elements are extensively bonded to the skin field or base element, and transport mainly axial loads. The skin field transports primarily shear loads, wherein by means of the extensive bonding of the longitudinal stiffe...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
Patent Type & Authority Patents(United States)
IPC IPC(8): B32B38/10B29C70/24B29D99/00B64C1/12B29C70/86B32B5/12B32B7/04B64C1/00B29K105/24B29L31/30
CPCB32B38/10B29C70/24B29C70/86B29D99/001B29D99/0014B32B5/12B64C1/12B32B7/04Y10T428/23914B29K2105/24B29K2105/246B29L2031/3082B29L2031/3085B64C2001/0072Y02T50/40
Inventor ELBRACHT, DIRK
Owner AIRBUS OPERATIONS GMBH
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com